On the roll–coupling instabilities of high–performance aircraft

Abstract

Restricted accessMoreSectionsView PDF ToolsAdd to favoritesDownload CitationsTrack Citations ShareShare onFacebookTwitterLinked InRedditEmail Cite this article Jahnke Craig C. 1998On the roll–coupling instabilities of high–performance aircraftPhil. Trans. R. Soc. A.3562223–2239http://doi.org/10.1098/rsta.1998.0271SectionRestricted accessOn the roll–coupling instabilities of high–performance aircraft Craig C. Jahnke Craig C. Jahnke Department of Mechanical, Aerospace and Manufacturing Engineering, Polytechnic University, Brooklyn, NY 11201, USA Google Scholar Find this author on PubMed Search for more papers by this author Craig C. Jahnke Craig C. Jahnke Department of Mechanical, Aerospace and Manufacturing Engineering, Polytechnic University, Brooklyn, NY 11201, USA Google Scholar Find this author on PubMed Search for more papers by this author Published:15 October 1998https://doi.org/10.1098/rsta.1998.0271AbstractHigh–performance aircraft configurations, characterized by a small span and swept wings, have rolling moments of inertia that are significantly smaller than the pitching or yawing moments of inertia. As a result, nonlinear coupling during high–roll–rate manoeuvres produces significant yawing and pitching moments. For certain critical flight conditions, inertial coupling causes jump phenomena called roll–coupling instabilities. These jump phenomena typically occur as a result of turning–point bifurcations of the aircraft steady states. Analysis of the moment balances along the steady solution branches provides physical insight into the causes of these instabilities and potential means of eliminating them. Analysis performed by using the full eight–degree–of–freedom equations of motion shows that the critical control–surface deflections are essentially the same as for the fifth– and sixth–order equations of motion. Solving the full eight–degree–of–freedom equations allows one to determine the orientation of the aircraft before and after the instability. For the aircraft model studied here, roll–coupling instabilities result in a change in sign of the angle of attack of the aircraft. The equilibrium state of the aircraft changes from a spiral dive, with the bottom of the aircraft closest to the axis of the spiral, to a spiral dive where the top of the aircraft is nearest the axis of the spiral, or vice versa depending on the trim angle of attack from which the manoeuvre was initiated. Pitching moment balance is shown to be central to the instability. Previous ArticleNext Article VIEW FULL TEXT DOWNLOAD PDF FiguresRelatedReferencesDetailsCited by Taha H and Hassan A (2021) Nonlinear Flight Physics of the Lie-Bracket Roll Mechanism AIAA Scitech 2021 Forum, 10.2514/6.2021-0252, 978-1-62410-609-5, Online publication date: 11-Jan-2021. Khatri A, Singh J and Sinha N (2012) Aircraft Maneuver Design Using Bifurcation Analysis and Sliding Mode Control Techniques, Journal of Guidance, Control, and Dynamics, 10.2514/1.56361, 35:5, (1435-1449), Online publication date: 1-Sep-2012. Hann C, Snowdon M, Rao A, Winn O, Wongvanich N and Chen X (2011) Minimal modelling approach to describe turbulent rocket roll dynamics in a vertical wind tunnel, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 10.1177/0954410011420771, 226:9, (1042-1060), Online publication date: 1-Sep-2012. Paranjape A, Sinha N and Ananthkrishnan N (2007) Use of Bifurcation and Continuation Methods for Aircraft Trim and Stability Analysis - A State-of-the-Art 45th AIAA Aerospace Sciences Meeting and Exhibit, 10.2514/6.2007-1051, 978-1-62410-012-3, Online publication date: 8-Jan-2007. Sibilski K (2006) Prediction of Helicopter Critical Flight Regimen by Continuation and Bifurcation Methods AIAA Atmospheric Flight Mechanics Conference and Exhibit, 10.2514/6.2006-6633, 978-1-62410-045-1, Online publication date: 21-Aug-2006. Sinha N and Ananthkrishnan N (2002) Maximum Steady Roll Rate in Zero-Sideslip Roll Maneuvers of Aircraft, Journal of Aircraft, 10.2514/2.3014, 39:5, (897-899), Online publication date: 1-Sep-2002. Nowakowski M, Sibilski K, Sibilska-Mroziewicz A and Żyluk A (2021) Bifurcation Flight Dynamic Analysis of a Strake-Wing Micro Aerial Vehicle, Applied Sciences, 10.3390/app11041524, 11:4, (1524) This Issue15 October 1998Volume 356Issue 1745Theme Issue ‘Nonlinear flight dynamics of high-performance aircraft’ compiled by J. M. T. Thompson and F. B. J. Macmillen Article InformationDOI:https://doi.org/10.1098/rsta.1998.0271Published by:Royal SocietyPrint ISSN:1364-503XOnline ISSN:1471-2962History: Published online15/10/1998Published in print15/10/1998 License: Citations and impact Keywordscontrol lossbifurcationaircraftinstabilityroll-couplingdynamics